BR0100845A - Methods and apparatus for retaining flow restrictors within turbine engines - Google Patents

Methods and apparatus for retaining flow restrictors within turbine engines

Info

Publication number
BR0100845A
BR0100845A BR0100845-5A BR0100845A BR0100845A BR 0100845 A BR0100845 A BR 0100845A BR 0100845 A BR0100845 A BR 0100845A BR 0100845 A BR0100845 A BR 0100845A
Authority
BR
Brazil
Prior art keywords
flow restrictor
methods
turbine engines
flow restrictors
orifice
Prior art date
Application number
BR0100845-5A
Other languages
Portuguese (pt)
Other versions
BR0100845B1 (en
Inventor
Matthew Kaminske
Original Assignee
Gen Electric
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Gen Electric filed Critical Gen Electric
Publication of BR0100845A publication Critical patent/BR0100845A/en
Publication of BR0100845B1 publication Critical patent/BR0100845B1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

Patente de Invenção: "MéTODOS E APARELHO PARA RETERRESTRITORES DE FLUXO DENTRO DE MOTORES DETURBINA". Um restritor de fluxo (40) inclui um corpo (46) quepermite que o restritor de fluxo seja auto-retido dentro de um orifíciopara sangria (80). Os orifícios para sangria são localizados sobrevárias partes de um motor de turbina a gás (10) e se estendeatravés de um invólucro de motor (90). O corpo restritor de fluxoinclui um orifício (50) que se estende entre tal primeira extremidadee tal segunda extremidade (42 e 44). Uma fenda (70) estende-se apartir de uma superfície externa (48) do corpo restritor de fluxo parao orifício. Durante a montagem, a fenda permite que o restritor defluxo se expanda e se conforme contra o orifício para sangria.Invention Patent: "METHODS AND APPLIANCE FOR FLOW RETERRESTRITORS INSIDE DETURBINE ENGINES". A flow restrictor (40) includes a body (46) that allows the flow restrictor to be self-contained within a bleed port (80). The bleed holes are located over parts of a gas turbine engine (10) and extend through an engine casing (90). The flow restrictor body includes an orifice (50) extending between such a first end and such a second end (42 and 44). A slot (70) extends from an external surface (48) of the flow restrictor body to the orifice. During assembly, the slot allows the flow restrictor to expand and conform to the bleed hole.

BRPI0100845-5A 2000-03-03 2001-03-05 method for mounting a gas turbine engine, gas turbine engine, and bleed port assembly for the engine. BR0100845B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/517,646 US6327844B1 (en) 2000-03-03 2000-03-03 Methods and apparatus for retaining flow restrictors within turbine engines

Publications (2)

Publication Number Publication Date
BR0100845A true BR0100845A (en) 2001-10-30
BR0100845B1 BR0100845B1 (en) 2009-08-11

Family

ID=24060640

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0100845-5A BR0100845B1 (en) 2000-03-03 2001-03-05 method for mounting a gas turbine engine, gas turbine engine, and bleed port assembly for the engine.

Country Status (6)

Country Link
US (1) US6327844B1 (en)
EP (1) EP1130305B1 (en)
JP (1) JP2001263005A (en)
BR (1) BR0100845B1 (en)
CA (1) CA2338648C (en)
DE (1) DE60112631T2 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10119468B2 (en) * 2012-02-06 2018-11-06 United Technologies Corporation Customer bleed air pressure loss reduction
FR3000521B1 (en) * 2012-12-27 2014-12-19 Snecma RECOVERY LINK TUBE
FR3000522B1 (en) * 2012-12-27 2018-11-02 Safran Aircraft Engines DOUBLE TUBE CONNECTION DEVICE
US9151429B2 (en) 2013-06-05 2015-10-06 Hamilton Sundstrand Corporation Flow restrictor
EP2881548B1 (en) 2013-12-09 2018-08-15 MTU Aero Engines GmbH Gas turbine compressor
US10443498B2 (en) * 2014-08-15 2019-10-15 United Technologies Corporation Gas turbine engine cooling fluid metering system
US10100730B2 (en) * 2015-03-11 2018-10-16 Pratt & Whitney Canada Corp. Secondary air system with venturi

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2499315A (en) * 1944-07-11 1950-02-28 Corydon M Johnson Rivet
US2808996A (en) * 1954-09-15 1957-10-08 Poor & Co Boltless rail joint
JPS5018862U (en) * 1973-06-15 1975-03-03
US3972641A (en) * 1974-04-04 1976-08-03 United Technologies Corporation Compressor bleed sensor and control for turbine type power plants
US4230436A (en) * 1978-07-17 1980-10-28 General Electric Company Rotor/shroud clearance control system
US5187931A (en) * 1989-10-16 1993-02-23 General Electric Company Combustor inner passage with forward bleed openings
US4919108A (en) * 1989-11-08 1990-04-24 Browning Cable guard assembly for compound bows
US5472313A (en) * 1991-10-30 1995-12-05 General Electric Company Turbine disk cooling system
US5275534A (en) * 1991-10-30 1994-01-04 General Electric Company Turbine disk forward seal assembly
US5224818A (en) * 1991-11-01 1993-07-06 General Electric Company Air transfer bushing
JP3387227B2 (en) * 1994-08-15 2003-03-17 石川島播磨重工業株式会社 Turbo engine
US5609467A (en) * 1995-09-28 1997-03-11 Cooper Cameron Corporation Floating interturbine duct assembly for high temperature power turbine
DE19815168C2 (en) * 1998-04-04 2001-02-22 Man Turbomasch Ag Ghh Borsig Piping through two or more walls of an axial compressor of a gas turbine
US6035627A (en) * 1998-04-21 2000-03-14 Pratt & Whitney Canada Inc. Turbine engine with cooled P3 air to impeller rear cavity

Also Published As

Publication number Publication date
DE60112631D1 (en) 2005-09-22
CA2338648A1 (en) 2001-09-03
US6327844B1 (en) 2001-12-11
BR0100845B1 (en) 2009-08-11
EP1130305A3 (en) 2003-11-12
EP1130305A2 (en) 2001-09-05
JP2001263005A (en) 2001-09-26
EP1130305B1 (en) 2005-08-17
CA2338648C (en) 2008-02-19
DE60112631T2 (en) 2006-06-14

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 05/03/2001, OBSERVADAS AS CONDICOES LEGAIS.

B24C Patent annual fee: request for for restoration

Free format text: REFERENTE A 11A ANUIDADE(S), CONFORME ART. 87 DA LPI 9.279.

B24H Lapse because of non-payment of annual fees (definitively: art 78 iv lpi)
B24F Patent annual fee: publication cancelled

Free format text: ANULADA A PUBLICACAO CODIGO 24.8 NA RPI NO 2259 DE 22/04/2014 POR TER SIDO INDEVIDA.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time

Free format text: REFERENTE A 11A ANUIDADE.

B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)

Free format text: EM VIRTUDE DA EXTINCAO PUBLICADA NA RPI 2607 DE 22-12-2020 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDA A EXTINCAO DA PATENTE E SEUS CERTIFICADOS, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.